EMG 2307: FLUID MECHANICS III
COMPRESSIBLE FLOWS
TUTORIAL
1. Air enters a nozzle at a pressure of 10 x 105 N/m2 and 270C with a velocity of 25 m/s. The
exit pressure is 5 x 105 N/m2. The flow follows the law (𝑝⁄𝜌𝛾 ) = constant. Determine the
velocity at exit. Take cp = 1003 J/kg K
2. A fighter aircraft is flying ata height where the temperature is -200C. Fligh Mach number
is 1.7. Assuming the properties of air as 𝛾 = 1.4 and R = 287 J/kg K. Determine the flight
speed.
3. A projectile is passing through a location where the pressure is 2 x 104 N/m2 and the
temperature -300C. If it was speeding at M = 2.2. Calculate the pressure, temperature and
density at the tip of projectile nose. Take 𝛾 = 1.4.
4. The stagnation conditions of air flowing through a nozzle are T0 = 450 K, P0 = 10 x 105
N/m2. Determine the value of (m/A) at the location where p = 8 x 105 N/m2. Assume
isentropic flow, 𝛾 = 1.4 and R = 287 J/kg K.